Propeller blade pivot

ABSTRACT

The invention relates to the field of aerial propellers, in particular the field of variable-pitch propellers, specifically for unducted fans. More specifically, the invention relates to a pivot ( 15 ) for a blade ( 14 ) of a propeller ( 3   a,    3   b ), the pivot including at least a proximal portion ( 15   a ) made of metal and suitable for being retained in a radial orifice of a propeller hub, while being capable of turning in said orifice about a longitudinal axis (Z) of the pivot ( 15 ), and a distal portion ( 15   b ) including a receptacle ( 20 ) suitable for retaining a blade root, and at least one arm ( 17 ) of organic matrix composite material extending laterally relative to said longitudinal axis (Z) and supporting a flyweight ( 16 ).

CROSS-REFERENCE TO RELATED APPLICATIONS

This application is a continuation of U.S. application Ser. No.14/279,727 filed May 16, 2014, the entire contents of which isincorporated herein by reference. U.S. application Ser. No. 14/279,727claims the benefit of priority from prior French Application No. 1354427 filed May 17, 2013.

BACKGROUND OF THE INVENTION

The present invention relates to the field of aerial propellers, andmore particularly to a propeller blade pivot.

In the present context, the term “aerial propeller” is used broadly tocover any device having at least one profiled blade suitable forrotating about a propulsion axis in order to accelerate a mass of airalong the direction of said propulsion axis so as to generate thrust inthe opposite direction by reaction. The term thus covers, amongst otherthings, conventional aviation propellers, and also turbojet fans,including unducted or open rotor fans. Typically, such unducted fanscomprise two contrarotating variable-pitch propellers.

Typically, a variable-pitch propeller includes a pivot at the base ofeach blade to enable the blade to turn about its longitudinal axis. Thepivot may be incorporated in the root of the blade or it may bedetachable from the blade, thereby making it easier to replace bladesand helping to reduce repair and maintenance costs.

Ideally, variable-pitch propellers include devices that actautomatically to enable them to be feathered in the event of the enginestopping. In particular, when the blades are feathered, the relativewind can still exert an aerodynamic torque on each blade about itslongitudinal axis. In order to oppose that aerodynamic torque and keepthe blades in a feathered orientation, one of the simplest devices knownto the person skilled in the art comprises a flyweight at the end of alever arm that extends laterally relative to said longitudinal axis, andperpendicularly to the pressure and/or suction faces of the blade. Thecentrifugal force exerted on each flyweight by the propeller rotatingserves to maintain the blade in the feathered orientation. In order tolimit their size, such flyweights and lever arms are typicallyincorporated in the pivot of each blade. French patent FR 2 957 329discloses an unducted fan turbojet having two contrarotating propellersin which the pivot of each blade has a device of that type for holdingthe blades in the feathered position.

Aerial propellers, and more particularly unducted fan propellers thatare normally driven by free turbines of the turbojet, can rotate atspeeds that are very high, thereby generating large traction forces onthe pivots. The pivots are typically made of metal and they aredimensioned to withstand such loads, and consequently they are ofconsiderable weight.

OBJECT AND SUMMARY OF THE INVENTION

The present invention description seeks to reduce the weight ofpropeller blade pivots, and in particular of a pivot of a propellerblade having at least a proximal portion suitable for being retained ina radial orifice of a propeller hub while allowing the blade to turn insaid orifice about a longitudinal axis of the pivot, together with adistal portion including a receptacle suitable for retaining a bladeroot, and also at least one arm extending laterally relative to saidlongitudinal axis and supporting a flyweight.

In at least one embodiment, the object of obtaining a pivot ofrelatively reduced weight is obtained by the fact that at least saidproximal portion is made of metal, whereas at least said arm is made ofan organic matrix composite material. Since the arm is stressed mainlyin bending during operation of the propeller, using organic matrixcomposite materials for making this member enables a significant savingin weight to be obtained for mechanical properties that are comparableor superior.

In order to ensure that forces are taken up in the connection with theblade root and in order to avoid force peaks in the composite material,which peaks could in particular give rise to delamination phenomena,said receptacle for receiving the blade root is made of metal.

In a first alternative, the receptacle may be formed in a metal insertthat is incorporated in the distal portion of the pivot. In particular,the metal insert may be incorporated in a preform for the distal portionof the pivot before curing a thermosetting resin that impregnates thepreform in order to form the matrix of an organic matrix compositematerial. Nevertheless, in an alternative, it is also possible toenvisage integrating the metal insert in the distal portion of the pivotafter the resin has been cured. In order to transmit forces between theproximal and distal portions of the pivot, they may be bonded togetherby adhesive or by a bolted connection, for example.

In a second alternative, the receptacle may be formed in a metalextension of the proximal portion of the pivot, so as to facilitate thetransmission of traction forces through the pivot. In particular, thismetal extension may pass through the distal portion of the pivot,thereby making it easier to integrate the distal and proximal portions.In order to retain the distal portion of the pivot better againstcentrifugal forces while the propeller is rotating, the metal extensionof the extension of the proximal portion of the pivot may present alongitudinal section that diverges towards a distal end of the pivot,thereby taking up the centrifugal forces by interlocking shapes.

The receptacle for receiving the blade root may be in the form of a slotof dovetail section oriented in a direction that is substantiallyperpendicular to the at least one arm. Thus, the blade root, whichpresents a section complementary to the dovetail section of the slot,can easily be inserted in or extracted from the receptacle along thedirection of said slot, the dovetail section of the slot serving toretain the blade against centrifugal forces while the propeller isrotating. The pivot may also include releasable latches enabling theblade root to be prevented from moving in the slot once it has beeninserted.

The pivot may include two opposite arms extending laterally relative tosaid longitudinal axis and each supporting a respective flyweight. Bydistributing the flyweights over two opposite arms, it is possible toreduce the bending load on each arm significantly, thereby enabling thetotal weight to be reduced.

The invention also provides a variable-pitch propeller comprising a hub,a plurality of such pivots radially received in the hub, and a bladefastened to each pivot, and the invention also relates to a fan, inparticular an unducted fan comprising at least one such propeller. Thefan may in particular comprise two contrarotating propellers, eachhaving such pivots. Furthermore, the invention also relates to aturbojet having such a fan, and to an aircraft propelled by at least onesuch turbojet.

BRIEF DESCRIPTION OF THE DRAWINGS

The invention can be well understood and its advantages appear better onreading the following detailed description of several embodiments givenas non-limiting examples. The description refers to the accompanyingdrawings, in which:

FIG. 1 is a diagram of an aircraft propelled by turbojets with unductedfans;

FIGS. 2A and 2B are diagrammatic longitudinal section views of twovariants of unducted fan turbojets, each having two variable-pitchcontrarotating propellers;

FIG. 3 is a diagram showing the operation of a pivot includingflyweights for keeping a variable-pitch propeller blade featheredagainst an aerodynamic torque caused by relative wind;

FIG. 4 is a perspective view of a variable-pitch propeller blade pivotin a first embodiment of the invention;

FIG. 5 is a longitudinal section view of the FIG. 3 pivot on plane V-V;

FIG. 6 shows a step in assembling the FIG. 3 pivot;

FIG. 7 is a longitudinal section view of a variable-pitch propellerblade pivot in a second embodiment of the invention;

FIG. 8 is a side view of a variable-pitch propeller blade pivot in athird embodiment of the invention;

FIG. 9 is an exploded perspective view of a variable-pitch propellerblade pivot in a fourth embodiment;

FIG. 10 shows a first step in assembling the FIG. 9 pivot;

FIG. 11 shows a second step in assembling the FIG. 9 pivot; and

FIG. 12 shows a third step in assembling the FIG. 9 pivot.

DETAILED DESCRIPTION OF THE INVENTION

Turbojets having an unducted fan, also known as an open rotor, are veryadvantageous for propelling aircraft because of their high fuelefficiency. FIG. 1 shows an aircraft 1 with two turbojets 2 withunducted fans 3 in the “pusher” position.

As shown in FIGS. 2A and 2B, such a turbojet 2 with an unducted fan 3comprises a gas generator 4 and an unducted fan 3 coupled to a highpressure turbine 5 downstream from the gas generator 4. In the twoexamples shown, the gas generator 4 comprises a first compressor stage6, a second compressor stage 7, a combustion chamber 8, a first highpressure turbine stage 9, and a second high pressure turbine stage 10.The first compressor stage 6 and the second high pressure turbine stage10 are coupled together in rotation by a first shaft 11, while thesecond compressor stage 7 and the first high pressure turbine stage 9are coupled together in rotation by a second shaft 12 mounted coaxiallyaround the first shaft 11. Thus, in operation, air entering via anupstream inlet of the first compressor stage 6 is compressed insuccession in the first and second compressor stages 6 and 7 prior toreaching the combustion chamber 8, into which fuel is injected andburnt. The hot gas resulting from this combustion is then expanded insuccession in the first and second high pressure turbine stages 9 and 10in order to drive the compressor stages 6 and 7. Because of the heatenergy imparted to this gas by the combustion, the combustion gasnevertheless remains sufficiently energetic downstream from the secondhigh compressor turbine stage 10 to drive a low pressure turbine 5 thatdrives the unducted fan 3.

FIGS. 2A and 2B show two alternative arrangements for driving theunducted fan 3. In both arrangements, the unducted fan 3 has twocontrarotating propellers 3 a and 3 b on the same axis. Nevertheless, inthe first variant, shown in FIG. 2A, the two propellers 3 a and 3 b arecoupled via a common speed-reducing gearbox 13 to at least one stage 5 aof the low pressure turbine 5, whereas in the second variant, as shownin FIG. 2B, each of the two propellers 3A and 3B is driven directly by arespective stage of the low pressure turbine 5, and they are not coupledto each other. In the second arrangement, the propellers 3 a and 3 b cannormally reach high speeds of rotation, thereby generating largecentrifugal forces, in particular at the root of each blade of thepropellers 3 a and 3 b.

In both of the variants shown, the propellers 3 a and 3 b arevariable-pitch propellers, i.e. each blade can pivot about alongitudinal axis in order to adapt the orientation of the leading edgeof the blade to the engine speed and/or to commands from the pilot. Forthis purpose, each blade 14 is mounted on a pivot 15, as shown in FIG.3. In particular, in the event of an engine failure, it is advantageousfor the blade 14 to be feathered, i.e. to have an angle of attack thatis substantially zero relative to the relative wind v_(r). It is thuspossible to prevent the relative wind causing the propeller to turn,since that leads to additional drag and can even cause the propeller tobe subjected to overspeed with negative consequences for the structuralintegrity of the turbojet 1 as a whole.

It is particularly desirable for each propeller 3 a, 3 b to includepassive means for keeping each blade 14 feathered even in the event of afailure of devices for varying the pitch of the propeller, which devicesare typically hydraulic or electrical. The center of thrust L of eachblade 14 may be offset relative to the pivot axis Z of the pivot 15,thereby generating an aerodynamic torque M_(a) tending to cause theblade 14 to pivot. In addition, an inertial torque M_(i) is alsogenerated, because of the center of gravity G of the blade 14 beingoffset from the pivot axis Z. To oppose these torques M_(a) and M_(i)and to keep the blade 14 feathered, flyweights 16 are suspended fromarms 17 that extend laterally relative to the pivot axis Z. Theorientation of these arms 17 is substantially perpendicular to thepressure and suction sides of the blade 14 such that when the propeller3 a, 3 b is rotating about its axis of rotation X, the centrifugalforces F_(C) acting on the flyweights 16 tend to bring the maindirection Y′ of the arms 17 into alignment with a direction Y that istangential relative to the propeller 3 a, 3 b, thereby opposing theaerodynamic and inertial torques M_(a) and M_(i) and bringing the bladeback into alignment with the direction of the relative wind v_(r).

FIG. 4 shows a propeller blade pivot 15 in a first embodiment of theinvention. This pivot 15 comprises a proximal portion 15 a and a distalportion 15 b. The proximal portion 15 a is made of metal. Morespecifically, in the example shown, this proximal portion 15 a is madeof light metal alloy. It is substantially axisymmetric in shape withradial shoulders, so as to enable it to be inserted in a radial orificeof a propeller hub, and so as to enable it to be retained in the orificewhile allowing the pivot 15 to turn relative to the orifice about thepivot axis Z.

In a first embodiment, the distal portion 15 b of the pivot 15 comprisesa metal extension 18 of the proximal portion 15 a. This extension 18 isformed integrally with the proximal portion 15 a and is received in acentral orifice passing through a part 19 made of organic matrixcomposite material. This composite part 19 includes the arms 17 havingthe flyweights 16 mounted at the ends thereof. The organic matrixcomposite material of this part 19 comprises fibers embedded in anorganic matrix, and more specifically in a polymer matrix. The fibersmay in particular be carbon fibers, although it is also possible toenvisage using other types of fiber, such as for example: glass fibers;polyamide fibers; or polyethylene fibers. These fibers may be arrangedin unidirectional layers or in layers that are woven in two-dimensions,and they may be laminated, or alternatively they may bethree-dimensionally woven. In order to take up bending forces better onthe arms 17, these fibers may be oriented mainly along the direction ofthe arms 17, at least in the proximity of the bottom faces of the arms17. The fibers are embedded in an organic matrix, more specifically apolymer matrix, which may in particular be constituted by athermosetting resin, such as an epoxy resin, or some other thermosettingresin that is better adapted to high temperatures. The composite part 19may be formed by resin transfer molding or by laminating fiber layersthat have been pre-impregnated with resin.

As can be seen in FIG. 4, the metal extension 18 of the proximal portion15 a of the pivot 15 is flush with the distal end of the pivot 15. Itpresents a receptacle 20 in the form of a slot of rounded dovetailcross-section oriented along a direction X′ that is substantiallyperpendicular to the pivot axis Z and to the main direction Y′ of thearms 17 for the purpose of receiving the root of the blade 14 (drawn indashed lines). After the blade root has been inserted in this receptacle20 along the direction X′ of the slot, it can be prevented form movingin this direction by transverse latches (not shown) in the receptacle20. The dovetail section of the receptacle 20 serves to take upcentrifugal forces exerted on the blade 14 along the direction of thepivot axis Z, while coupling the blade 14 to the pivot 15 for turningabout the pivot axis Z.

The metal extension 18 presents two lateral protuberances 21 extendingin the main direction Y′ of the arms 17. These two oppositeprotuberances 21 are of a shape such that said metal extension 18presents a longitudinal section in the plane V-V shown in FIG. 5 thatdiverges towards the distal end of the pivot 15. Thus, these lateralprotuberances 21 form shoulders that by interlocking shapes are suitablefor taking up centrifugal forces along the direction of the pivot axis Zas transmitted by the arms 17 when the propeller 3 a, 3 b is rotating.

FIG. 6 shows how the composite part 19 is assembled with the proximalportion 15 a of the pivot 15 and shows its metal extension 18 forforming the pivot 15 in this first embodiment. At this stage ofassembly, the proximal portion 15 a of the pivot 15 is inserted throughthe orifice 22 into the composite part 19 until the lateralprotuberances 21 of the metal extension 18 come to bear againstcomplementary inside surfaces of the orifice 22. A layer of adhesivebetween the outside surfaces of the metal extension 18 and the insidesurfaces of the orifice 22 serves to provide adhesion between the metalextension 18 and the composite part 19.

FIG. 7 shows a second embodiment in which the proximal portion 15 a ofthe pivot 15 does not have a metal extension passing through the topportion 15 b. This embodiment also presents a receptacle 20 in the formof a slot of rounded dovetail cross-section extending along a directionX′ substantially perpendicular to the pivot axis Z and to the main axisY′ of the arm 17, for the purpose of receiving the root of the blade 14.Nevertheless, this receptacle 20 is formed in a metal insert 23incorporated in the composite part 19 without any direct contact withthe bottom portion 15 a of the pivot. The remaining elements of thepivot 15 are nevertheless analogous to those of the first embodiment andconsequently they are given the same reference numbers in the drawings.In this second embodiment, the metal proximal portion 15 a of the pivot15 and the composite part 19 are bonded together by adhesive.

FIG. 8 shows a third embodiment similar to the second, but in which theproximal portion 15 a of the pivot 15 and the composite part 19 arebonded together by a bolted connection 24 formed by a plate 25 bearingagainst the distal end of the pivot 15, and by bolts 26 connecting theplate 25 to the metal proximal portion 15 a. The remaining elements ofthis pivot 15 are nevertheless analogous to those of the secondembodiment and consequently they are given the same reference numbers inthe drawings.

FIG. 9 shows a fourth embodiment in which the proximal portion 15 a ofthe pivot 15 presents, as in the first embodiment, a metal extension 18passing through the composite part 19 in the distal portion 15 b.Nevertheless, in this fourth embodiment, the receptacle 20 for receivingthe root of the blade 14 is not formed directly in this metal extension18, but rather in a metal insert 23 similar to the insert of the secondand third embodiments. In addition, in this fourth embodiment, the metalinsert 23 contributes together with bolts 32 and 33 to provide themechanical connection between the proximal portion 15 a with itsmechanical extension 18 and the composite part 19 of the distal portion15 b of the pivot 15. This composite part 19 is received in a concaveportion of the metal extension 18 that is open in the distal direction.The contact surfaces between the metal extension 18 and the compositepart 19 presents a shape that is suitable for co-operating to provideblocking between them in a plane that is substantially perpendicular tothe pivot axis Z. Thus, in the embodiment shown, the shoulders 27prevent the composite part 19 from moving relative to the metalextension 18 in the main direction Y′ of the arms 17, whereas othershoulders 28 that are perpendicular prevent the composite part 19 frommoving relative to the metal extension 18 in the main direction X′ ofthe slot in the receptacle 20. Inside surfaces 29 and 30 respectively ofthe metal extension 18 and of the composite part 19 together form agroove 31 of rounded dovetail cross-section receiving the metal insert23, which itself presents a cross-section complementary to that of thegroove 31 and thus forms between them a latch providing interactingshapes that prevent movement in the direction of the pivot axis Z. Forthis purpose, these surfaces 29 and 30 are substantially in mutualalignment along the direction X′ and they are spaced apart on eitherside of a plane that is perpendicular or oblique relative to thisdirection X′. Finally, bolts 32 and 33 finish off making the connectionbetween the metal extension 18, the composite part 19, and the insert23. The first bolt 32 directly connects the insert 23 to the metalextension 18 outside the shoulders 28, while the second bolt 33 connectsthe insert 23 to the proximal portion 15 a via through orifices in thecomposite part 19 between the shoulders 28. The remaining elements inFIG. 9 correspond to analogous elements in the above-describedembodiments and consequently they are given the same reference numbers.

FIG. 10 shows a first step in assembling the pivot 15 in this fourthembodiment. In this first step, the composite part 19 with fibers thatmay be oriented mainly in the main direction Y′ of the arms 17, isreceived in the concave portion in the distal end of the metal extension18 and is prevented from moving in the plane perpendicular to the pivotaxis by the shoulders 27 and 28. Thereafter, in a second step shown inFIG. 11, the insert 23 is slid along the direction X′ in the groove 31.The dovetail shape of the cross-section of the this groove 31 thenprovides interacting shapes that prevent relative movement along thedirection of the pivot axis Z between the insert 23 and each of thesurfaces 29, 30 forming the groove 31. Finally, in a third step shown inFIG. 12, the bolts 32 and 33 are inserted and tightened in thecorresponding orifices, so as to retain the insert 23 in the groove 31.

Although the present invention is described above with reference tospecific embodiments, it is clear that various modifications and changesmay be made to these embodiments without going beyond the general ambitof the invention as defined by the claims. In addition, individualcharacteristics of these various embodiments described may be combinedin additional embodiments. Consequently, the description and thedrawings should be considered in a sense that is illustrative ratherthan restrictive.

1. A pivot for a blade of a propeller, the pivot comprising: a proximalportion made of metal and suitable to be retained in a radial orifice ina propeller hub while being capable of turning in this orifice about alongitudinal axis of the pivot; and a distal portion made of organicmatrix composite material incorporating a metal insert forming areceptacle for retaining a blade root, the distal portion furthercomprising at least one arm extending laterally relative to thelongitudinal axis of the pivot and supporting a flyweight; wherein ametal extension of the proximal portion presents shoulders locking thedistal portion with respect to the proximal portion in a planeperpendicular to the longitudinal axis of the pivot, and inside surfacesof the metal extension of the proximal portion and of a composite partof the distal portion align so as to form a dovetail groove receivingthe metal insert of the distal portion locking the distal portion withrespect to the proximal portion in the direction of the longitudinalaxis of the pivot.
 2. The pivot according to claim 1, further comprisinga bolted connection between the proximal and distal portions.
 3. Thepivot according to claim 1, wherein the metal extension of the proximalportion of the pivot passes through the distal portion of the pivot. 4.The pivot according to claim 1, wherein the receptacle is in the form ofa slot of dovetail section extending in a direction that issubstantially perpendicular to the at least one arm of the distalportion.
 5. The pivot according to claim 1, wherein the distal portioncomprises two opposite arms extending laterally relative to thelongitudinal axis of the pivot and each supporting a respectiveflyweight.
 6. A propeller comprising: a propeller blade; a propellerhub; and a pivot comprising: a proximal portion made of metal andretained in a radial orifice in the propeller hub while being capable ofturning in this radial orifice about a longitudinal axis of the pivot;and a distal portion made of organic matrix composite materialincorporating a metal insert forming a receptacle retaining a blade rootof the propeller blade, the distal portion further comprising at leastone arm extending laterally relative to the longitudinal axis of thepivot and supporting a flyweight; wherein a metal extension of theproximal portion presents shoulders locking the distal portion withrespect to the proximal portion in a plane perpendicular to thelongitudinal axis of the pivot, and inside surfaces of the metalextension of the proximal portion and of a composite part of the distalportion align so as to form a dovetail groove receiving the metal insertof the distal portion locking the distal portion with respect to theproximal portion in the direction of the longitudinal axis of the pivot.